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US 10,378,439 B2Granted
Gas turbine engine with variable speed turbines
AssigneeRolls-Royce North American Technologies Inc.
InventorsRobert W. Cedoz, Syed J. Khalid
Life of this patent
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Abstract
Embodiments of the present invention include unique gas turbine engines. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
Claims13
A gas turbine engine, comprising:
- a fan configured to generate and transmit a bypass flow in a bypass duct;
- a compressor in fluid communication with the fan;
- a combustor in fluid communication with the compressor;
- a first turbine in fluid communication with the combustor and operative to drive the compressor;
- a second turbine in fluid communication with the first turbine and operative to drive the fan, wherein the second turbine includes at least a first stage and a second stage downstream of the first stage, both the first and second stages operative to drive the fan;
- and
- a clutch configured to allow the first stage to rotate at a faster speed than the second stage,
- further comprising a valve fluidly disposed between the first stage and the second stage, wherein the valve is configured to vent an output of the first stage, thereby reducing an amount of gas that is delivered to the second stage and increasing a speed of the first stage,
- wherein the valve is configured as a sleeve valve,
- wherein the clutch is configured to prevent the second stage from rotating faster than the first stage.
7 more elements
A gas turbine engine, comprising:
- a compressor;
- a combustor in fluid communication with the compressor;
- a first turbine in fluid communication with the combustor and operative to drive the compressor;
- a second turbine in fluid communication with the first turbine and operative to drive a load absorber, wherein the second turbine includes at least a first stage and a second stage downstream of the first stage;
- and
- a valve fluidly disposed between the first stage and the second stage, wherein the valve is configured to vent an output of the first stage, thereby reducing an amount of gas that is delivered to the second stage and increasing a speed of the first stage,
- wherein the valve is configured as a sleeve valve,
- further comprising a clutch configured to allow the first stage to rotate at a faster speed than the second stage,
- wherein the clutch is configured to always prevent the second stage from rotating faster than the first stage.
6 more elements
A gas turbine engine, comprising:
- a compressor;
- a combustor in fluid communication with the compressor;
- a first turbine in fluid communication with the combustor and operative to drive the compressor;
- a second turbine in fluid communication with the first turbine and operative to drive a load absorber, wherein the second turbine includes at least a first stage and a second stage downstream of the first stage, both the first and second stages operative to drive the load absorber;
- and
- means for selectively increasing a speed of the first stage and decreasing a speed of the second stage or selectively operating both the first stage and the second stage at a same speed during operation of the gas turbine engine;
- wherein the means includes a sleeve valve fluidly disposed between the first stage and the second stage and operative to selectively vent an output of the first stage, thereby reducing an amount of gas that is delivered to the second stage and increasing the speed of the first stage, and a clutch configured to allow the first stage to rotate at a faster speed than the second stage,
- wherein the clutch is configured to always prevent the second stage from rotating faster than the first stage.
5 more elements
Dependencies are inferred from the claim text.